DE4427360B4 - Internally cooled blade of a turbine rotor blade of a gas turbine engine - Google Patents
Internally cooled blade of a turbine rotor blade of a gas turbine engine Download PDFInfo
- Publication number
- DE4427360B4 DE4427360B4 DE4427360A DE4427360A DE4427360B4 DE 4427360 B4 DE4427360 B4 DE 4427360B4 DE 4427360 A DE4427360 A DE 4427360A DE 4427360 A DE4427360 A DE 4427360A DE 4427360 B4 DE4427360 B4 DE 4427360B4
- Authority
- DE
- Germany
- Prior art keywords
- outlet
- blade
- turbine rotor
- internally cooled
- rotor blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000001816 cooling Methods 0.000 claims abstract description 17
- 230000007704 transition Effects 0.000 claims abstract 2
- 239000007789 gas Substances 0.000 description 6
- 239000000463 material Substances 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000005553 drilling Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000003082 abrasive agent Substances 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000009877 rendering Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Innengekühltes Blatt
(16) einer Turbinenrotorschaufel (10) eines Gasturbinenmotors, mit
– einer
Kopffläche
(32), einer voreilenden Kante (20), einer nacheilenden Kante (22)
und einer Druckseite (18),
– einer ringförmigen Abdeckung,
die konzentrisch um die Blätter
angeordnet ist und mit der Kopffläche (32) einen Spalt (48) begrenzt,
– einem
inneren Durchlass (52) zum Leiten von Kühlluft zu Auslässen (30),
die benachbart zur Kopffläche
(32) des Blattes (16) im Bereich der Druckseite (18) ausgebildet
sind und einen Kühlluftstrahl
(42) unter einem gegebenen Winkel (C) abgeben,
dadurch gekennzeichnet,
dass jeder der Auslässe
(30) in dem Übergang
zwischen der Druckseite (18) und der Kopffläche (32) in einer Ausnehmung
(36) mündet,
welch letztere sich von der Druckseite (18) in Richtung der Saugseite (24)
bis zur saugseitigen Wand des Auslasses und, gesehen in der Richtung
von der voreilenden Kante (20) zur nacheilenden Kante (22), im Wesentlichen über die
gesamte Breite des betreffenden Auslasses...An internally cooled blade (16) of a turbine rotor blade (10) of a gas turbine engine, with
A head surface (32), a leading edge (20), a trailing edge (22) and a pressure side (18),
An annular cover concentrically arranged around the blades and defining a gap (48) with the head surface (32),
An inner passage (52) for directing cooling air to outlets (30) formed adjacent to the top surface (32) of the blade (16) in the region of the pressure side (18) and a cooling air jet (42) at a given angle (C ) submit,
characterized in that each of the outlets (30) in the transition between the pressure side (18) and the head surface (32) in a recess (36) opens, which latter from the pressure side (18) in the direction of the suction side (24) to to the suction-side wall of the outlet and, viewed in the direction from the leading edge (20) to the trailing edge (22), substantially over the entire width of the outlet in question ...
Description
Die Erfindung betrifft ein innengekühltes Blatt einer Turbinenrotorschaufel eines Gasturbinenmotors, mit den im Oberbegriff des Anspruches 1 angegebenen Merkmalen.The The invention relates to an internally cooled Blade of a turbine rotor blade of a gas turbine engine, with the specified in the preamble of claim 1 features.
Auf dem Gebiet der Gasturbinenmotortechnik ist es bekannt, dass große Anstrengungen unternommen wurden, um die Maschinennutzleistung zu verbessern, indem versucht wird, das Spiel des Spaltes zwischen der äußeren Luftdichtung und dem Kopf der Turbinenschaufel über den vollen Bereich des Maschinenbetriebs auf einem Minimum zu halten. Im Laufe der Jahre wurden zur Erreichung dieses Ziels eine Vielzahl von Erfindungen gemacht und Konzepte entwickelt, um den Spalt passiv oder aktiv genau zu steuern.On In the field of gas turbine engine technology, it is known that great efforts have been undertaken to improve machine performance, by trying the game of the gap between the outer air seal and the head of the turbine blade over the full range of engine operation to keep to a minimum. Over the years have been reaching This goal made a variety of inventions and concepts designed to passively or actively control the gap accurately.
Bis zu einem gewissen Grad haben sich viele dieser Erfindungen und Konzepte als erfolgreich erwiesen. Wegen des zunehmenden Bedarfs an Antriebs- und Fluggerätenutzleistung, ist das Problem jedoch immer schwieriger geworden. Die Lösung des Problems wird außerdem durch die Art der Auslegung des Fluggeräts und/oder des Antriebs sowie seine spezielle Bestimmung geprägt. Was beispielsweise für ein Zivilflugzeug zufriedenstellend ist, ist meist für ein Militärflugzeug, insbesondere für ein Kampfflugzeug, nicht zufriedenstellend.To To some extent, many of these inventions and concepts have become proved successful. Because of the increasing demand for propulsion and aircraft performance, However, the problem has become more and more difficult. The solution of the problem will also by the type of design of the aircraft and / or the propulsion and its special provision coined. What for example a civil aircraft is satisfactory, is mostly for a military aircraft, especially for a fighter, unsatisfactory.
Ein
innengekühltes
Blatt einer Turbinenrotorschaufel eines Gasturbinenmotors und mit
den Merkmalen des Oberbegriffes des Anspruches 1 ist aus der
Eine ähnliche
Konstruktion ist aus der
Der Erfindung liegt die Aufgabe zugrunde, ein gattungsgemäßes innengekühltes Blatt einer Turbinenrotorschaufel zu schaffen, dessen Kühlluftauslässe besser als bisher gegen Verschmutzung, Verstopfen und/oder Zusetzen der Kühlluftauslässe geschützt ist.Of the Invention is based on the object, a generic internally cooled sheet a turbine rotor blade whose cooling air outlets better than previously against pollution, clogging and / or clogging of Cooling air outlets is protected.
Diese Aufgabe ist bei einem solchen innengekühlten Blatt durch die im Kennzeichen des Anspruches 1 angegebenen Merkmale gelöst.These Task is with such an internally cooled sheet by the in the plate of claim 1 given characteristics.
Durch diese Konstruktion wird erreicht, dass die Auslässe einen Kühlluftstrom in den Spalt zwischen der äußeren Luftdichtung und dem Kopf des Blattes ausströmen lassen.By This design ensures that the outlets allow a flow of cooling air into the gap between the outer air seal and the head of the leaf to let.
Vorteilhafte Ausführungsformen sind in den Ansprüchen 1 bis 4 angegeben.advantageous embodiments are in the claims 1 to 4 indicated.
Nachfolgend wird die Erfindung anhand der Zeichnung beispielhaft näher erläutert; es zeigt:following the invention will be explained in more detail by way of example with reference to the drawing; it shows:
Ein
besseres Verständnis
der vorliegenden Erfindung ergibt sich aus den
Wie
in den
Wie
in den
Es
ist wichtig, dass die Oberfläche
Gemäß der Erfindung
ist der Winkel C, der zur Optimierung der Motornutzleistung auszulegen ist,
größer als
der Winkel bei den bekannten Konstruktionen, die keine Ausnehmung
Die
Gründe,
weshalb der optimale Winkel C für
die Löcher
Zweitens
vermag ein Hohlraum, wie die in
Drittens
tritt auf den Schaufeln, die sich im Reibeingriff mit der äußeren Luftdichtung
Die
Erfindung bezweckt, dass der Winkel der Fläche
Die
Ausnehmung
Durch die bevorzugten Ausführungsformen der Erfindung werden neben anderen die folgenden Verbesserungen erzielt:
- 1. Die Wahrscheinlichkeit, dass Kopfauslässe durch Schmiermaterial infolge von Schaufelkopfreibung verstopft werden, wird minimiert, wodurch sichergestellt ist, dass die Dichtungs- und Kühleigenschaften der Auslässe erhalten bleiben.
- 2. Die Herstellbarkeit der Auslässe wird durch Unempfindlichmachen des Leistungszuwachses in Bezug auf die Toleranz der Auslassposition relativ zur Druckseite des Blatts verbessert.
- 3. Die Kopfdichtungsfunktion wird verbessert, wenn der Winkel
C (
3 ) aufgrund von räumlichen Beschränkungen vergrößert werden muss. - 4. Kopfdichtungsauslasskonfigurationen lassen sich leichter herstellen, wenn die Schaufelkopfoberflächen mit schleifendem Material überzogen sind, das ein Problem beim Bohren von EDM-Löchern und/oder beim Abdecken der Auslässe hervorruft, wenn sie gebohrt werden.
- 1. The likelihood of plugging the head outlets by lubricating material due to blade head friction is minimized, ensuring that the sealing and cooling characteristics of the outlets are maintained.
- 2. The manufacturability of the outlets is improved by rendering the performance increase in terms of tolerance of the outlet position relative to the pressure side of the sheet insensitive.
- 3. The head sealing function is improved when the angle C (
3 ) must be increased due to spatial restrictions. - 4. Head seal outlet configurations are easier to fabricate when the blade head surfaces are coated with abrasive material that creates a problem in drilling EDM holes and / or covering the outlets as they are being drilled.
Claims (4)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US07/966,985 US5476364A (en) | 1992-10-27 | 1992-10-27 | Tip seal and anti-contamination for turbine blades |
GB9415591A GB2291935B (en) | 1992-10-27 | 1994-08-02 | Tip seal and anti-contamination for turbine blades |
DE4427360A DE4427360B4 (en) | 1992-10-27 | 1994-08-02 | Internally cooled blade of a turbine rotor blade of a gas turbine engine |
FR9409703A FR2723396B1 (en) | 1992-10-27 | 1994-08-04 | INTERNALLY COOLED SUSTENTATION PLAN OF A TURBINE ROTOR VANE OF A GAS TURBINE ENGINE AND PROCESS FOR MANUFACTURING THE VANE |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US07/966,985 US5476364A (en) | 1992-10-27 | 1992-10-27 | Tip seal and anti-contamination for turbine blades |
GB9415591A GB2291935B (en) | 1992-10-27 | 1994-08-02 | Tip seal and anti-contamination for turbine blades |
DE4427360A DE4427360B4 (en) | 1992-10-27 | 1994-08-02 | Internally cooled blade of a turbine rotor blade of a gas turbine engine |
FR9409703A FR2723396B1 (en) | 1992-10-27 | 1994-08-04 | INTERNALLY COOLED SUSTENTATION PLAN OF A TURBINE ROTOR VANE OF A GAS TURBINE ENGINE AND PROCESS FOR MANUFACTURING THE VANE |
Publications (2)
Publication Number | Publication Date |
---|---|
DE4427360A1 DE4427360A1 (en) | 1996-02-08 |
DE4427360B4 true DE4427360B4 (en) | 2007-08-09 |
Family
ID=27436027
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE4427360A Expired - Fee Related DE4427360B4 (en) | 1992-10-27 | 1994-08-02 | Internally cooled blade of a turbine rotor blade of a gas turbine engine |
Country Status (4)
Country | Link |
---|---|
US (1) | US5476364A (en) |
DE (1) | DE4427360B4 (en) |
FR (1) | FR2723396B1 (en) |
GB (1) | GB2291935B (en) |
Families Citing this family (38)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5771577A (en) * | 1996-05-17 | 1998-06-30 | General Electric Company | Method for making a fluid cooled article with protective coating |
US6027306A (en) * | 1997-06-23 | 2000-02-22 | General Electric Company | Turbine blade tip flow discouragers |
US5997251A (en) * | 1997-11-17 | 1999-12-07 | General Electric Company | Ribbed turbine blade tip |
US6086328A (en) * | 1998-12-21 | 2000-07-11 | General Electric Company | Tapered tip turbine blade |
US6190129B1 (en) | 1998-12-21 | 2001-02-20 | General Electric Company | Tapered tip-rib turbine blade |
US6179556B1 (en) | 1999-06-01 | 2001-01-30 | General Electric Company | Turbine blade tip with offset squealer |
US6478537B2 (en) * | 2001-02-16 | 2002-11-12 | Siemens Westinghouse Power Corporation | Pre-segmented squealer tip for turbine blades |
US6527514B2 (en) | 2001-06-11 | 2003-03-04 | Alstom (Switzerland) Ltd | Turbine blade with rub tolerant cooling construction |
US6790005B2 (en) | 2002-12-30 | 2004-09-14 | General Electric Company | Compound tip notched blade |
US6932571B2 (en) * | 2003-02-05 | 2005-08-23 | United Technologies Corporation | Microcircuit cooling for a turbine blade tip |
US7080971B2 (en) * | 2003-03-12 | 2006-07-25 | Florida Turbine Technologies, Inc. | Cooled turbine spar shell blade construction |
DE10355241A1 (en) * | 2003-11-26 | 2005-06-30 | Rolls-Royce Deutschland Ltd & Co Kg | Fluid flow machine with fluid supply |
US7118342B2 (en) * | 2004-09-09 | 2006-10-10 | General Electric Company | Fluted tip turbine blade |
US7510376B2 (en) * | 2005-08-25 | 2009-03-31 | General Electric Company | Skewed tip hole turbine blade |
US7287959B2 (en) * | 2005-12-05 | 2007-10-30 | General Electric Company | Blunt tip turbine blade |
US7686578B2 (en) * | 2006-08-21 | 2010-03-30 | General Electric Company | Conformal tip baffle airfoil |
US7607893B2 (en) * | 2006-08-21 | 2009-10-27 | General Electric Company | Counter tip baffle airfoil |
US8500396B2 (en) * | 2006-08-21 | 2013-08-06 | General Electric Company | Cascade tip baffle airfoil |
US8632311B2 (en) * | 2006-08-21 | 2014-01-21 | General Electric Company | Flared tip turbine blade |
US8512003B2 (en) | 2006-08-21 | 2013-08-20 | General Electric Company | Tip ramp turbine blade |
US8425183B2 (en) | 2006-11-20 | 2013-04-23 | General Electric Company | Triforial tip cavity airfoil |
US8186965B2 (en) * | 2009-05-27 | 2012-05-29 | General Electric Company | Recovery tip turbine blade |
US9091177B2 (en) | 2012-03-14 | 2015-07-28 | United Technologies Corporation | Shark-bite tip shelf cooling configuration |
US9284845B2 (en) | 2012-04-05 | 2016-03-15 | United Technologies Corporation | Turbine airfoil tip shelf and squealer pocket cooling |
US9228442B2 (en) | 2012-04-05 | 2016-01-05 | United Technologies Corporation | Turbine airfoil tip shelf and squealer pocket cooling |
US10655473B2 (en) | 2012-12-13 | 2020-05-19 | United Technologies Corporation | Gas turbine engine turbine blade leading edge tip trench cooling |
GB2529681B (en) | 2014-08-29 | 2019-02-20 | Rolls Royce Plc | Gas turbine engine rotor arrangement |
GB201417429D0 (en) * | 2014-10-02 | 2014-11-19 | Rolls Royce Plc | A cooled component |
US9995147B2 (en) * | 2015-02-11 | 2018-06-12 | United Technologies Corporation | Blade tip cooling arrangement |
US10107108B2 (en) | 2015-04-29 | 2018-10-23 | General Electric Company | Rotor blade having a flared tip |
USD844466S1 (en) | 2017-06-22 | 2019-04-02 | Unison Industries, Llc | Temperature sensor |
US10578498B2 (en) | 2017-06-22 | 2020-03-03 | Unison Industries, Llc | Air temperature sensor |
US10605675B2 (en) | 2017-06-22 | 2020-03-31 | Unison Industries, Llc | Air temperature sensor |
US10585007B2 (en) | 2017-06-22 | 2020-03-10 | Unison Industries, Llc | Air temperature sensor |
US10545057B2 (en) | 2017-06-22 | 2020-01-28 | Unison Industries, Llc | Air temperature sensor and method of reducing error |
US10605098B2 (en) | 2017-07-13 | 2020-03-31 | General Electric Company | Blade with tip rail cooling |
US11053848B2 (en) * | 2018-01-24 | 2021-07-06 | General Electric Company | Additively manufactured booster splitter with integral heating passageways |
JP6946225B2 (en) * | 2018-03-29 | 2021-10-06 | 三菱重工業株式会社 | Turbine blades and gas turbines |
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2105415A (en) * | 1981-09-02 | 1983-03-23 | Westinghouse Electric Corp | Air-cooled turbine rotor blade with trailing edge recessed holes |
US5261789A (en) * | 1992-08-25 | 1993-11-16 | General Electric Company | Tip cooled blade |
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US4676719A (en) * | 1985-12-23 | 1987-06-30 | United Technologies Corporation | Film coolant passages for cast hollow airfoils |
US4705455A (en) * | 1985-12-23 | 1987-11-10 | United Technologies Corporation | Convergent-divergent film coolant passage |
US4672727A (en) * | 1985-12-23 | 1987-06-16 | United Technologies Corporation | Method of fabricating film cooling slot in a hollow airfoil |
US4762464A (en) * | 1986-11-13 | 1988-08-09 | Chromalloy Gas Turbine Corporation | Airfoil with diffused cooling holes and method and apparatus for making the same |
US4827587A (en) * | 1988-01-25 | 1989-05-09 | United Technologies Corporation | Method of fabricating an air cooled turbine blade |
US5030060A (en) * | 1988-10-20 | 1991-07-09 | The United States Of America As Represented By The Secretary Of The Air Force | Method and apparatus for cooling high temperature ceramic turbine blade portions |
US5282721A (en) * | 1991-09-30 | 1994-02-01 | United Technologies Corporation | Passive clearance system for turbine blades |
US5313038A (en) * | 1992-12-22 | 1994-05-17 | United Technologies Corporation | EDM drilling of low angle holes |
-
1992
- 1992-10-27 US US07/966,985 patent/US5476364A/en not_active Expired - Lifetime
-
1994
- 1994-08-02 DE DE4427360A patent/DE4427360B4/en not_active Expired - Fee Related
- 1994-08-02 GB GB9415591A patent/GB2291935B/en not_active Expired - Fee Related
- 1994-08-04 FR FR9409703A patent/FR2723396B1/en not_active Expired - Fee Related
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2105415A (en) * | 1981-09-02 | 1983-03-23 | Westinghouse Electric Corp | Air-cooled turbine rotor blade with trailing edge recessed holes |
US5261789A (en) * | 1992-08-25 | 1993-11-16 | General Electric Company | Tip cooled blade |
Also Published As
Publication number | Publication date |
---|---|
FR2723396A1 (en) | 1996-02-09 |
GB2291935B (en) | 1999-02-24 |
US5476364A (en) | 1995-12-19 |
DE4427360A1 (en) | 1996-02-08 |
FR2723396B1 (en) | 1996-10-31 |
GB9415591D0 (en) | 1994-09-21 |
GB2291935A (en) | 1996-02-07 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
8110 | Request for examination paragraph 44 | ||
8364 | No opposition during term of opposition | ||
8339 | Ceased/non-payment of the annual fee |